• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A removable dynamic air turbine between a stowed position and an extended position is described comprising a rotatable hub module. A hub face is placed at the first end of the rotating hub. The face of the hub has a non-planar configuration so that a limited portion of the surface area of the hub face is placed in an aircraft oriented perpendicular to a direction of passage of an air flow. upstream of the hub face when the dynamic air turbine is in the deployed position.
    公开号:FR3027878A1
    申请号:FR1560396
    申请日:2015-10-30
    公开日:2016-05-06
    发明作者:Geoffrey D Fenelon；William E Seidel；Alan J Fahrner；Michael John Giamati；Gregory C Hopkins；Mark Walter Corcoran；Lubomir A Ribarov
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    [0001] ICE DELIVERY TOURNIQUET FOR A HISTORICAL DYNAMIC AIR TURBINE OF THE INVENTION [0001] Examples of embodiments of this invention generally relate to emergency power supplies for aeronautical applications, and more particularly to a module. improved dynamic air turbine engine to generate emergency power for an aircraft in flight. [0002] The aircraft comprise, in their standard equipment, a backup power source which must be used in the event of a power failure in the main power system. The emergency equipment is stored in a storage space inside the fuselage or the root of the aircraft. An example of such emergency equipment is a dynamic air turbine (RAT). During an emergency event, such as a power outage, e.g., the RAT is deployed in the air stream where the airflow relative to the speed of the aircraft causes rotation. turbine blades of the emergency equipment. A RAT can produce a hydraulic current, an electric current, or both. The turbine is coupled to appropriate power generation equipment, such as a hydraulic pump for the hydraulic power, or an electric generator for the electric power, or both in the case of a hybrid RAT. [0003] When the RAT is deployed in adverse ambient flight conditions, ice may form and accumulate on the RAT resulting in degradation of the component or system performance. In addition, loose parts of the accumulated ice pose a risk of being dragged into the airstream and causing further damage to any of the RAT components placed in the downstream path of flying ice fragments. .
    [0002] BRIEF DESCRIPTION OF THE INVENTION [0004] According to one embodiment of the invention, a dynamic air turbine removable between a stowed position and an extended position is described comprising a rotary hub. A hub face is placed at the first end of the rotating hub. The face of the hub has a non-planar configuration so that a limited portion of the surface area of the hub face is placed in an aircraft oriented perpendicular to a direction of passage of an air flow. upstream of the hub face when the dynamic air turbine is in the deployed position.
    [0003] BRIEF DESCRIPTION OF THE FIGURES [0005] The object of the invention, which is considered the invention, is particularly described and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the invention are apparent from the detailed description taken in conjunction with the accompanying drawings, in which: FIG. 1 is a schematic diagram of an exerfiple of a dynamic air turbine (RAT) of an aircraft; [0007] FIG. 2 is a perspective view of a RAT according to an embodiment of the invention; [0008] FIGS. 3a-3e are cross-sectional views of a plurality of hub faces of a rotary hub module of a RAT according to one embodiment of the invention; [0009] FIG. 4 is a side view of a rotary hub module of a RAT according to one embodiment of the invention; and [0010] FIGS. 5A and 5B are front views of a rotary hub module of a RAT according to one embodiment of the invention. The detailed description explains the embodiments of the invention, with the advantages and characteristics, by means of examples with reference to the illustrations. DETAILED DESCRIPTION OF THE INVENTION [0012] Referring now to FIGS. 1 and 2, an example of a dynamic air turbine (RAT) 10 having an associated deployment mechanism comprising a support 12 is illustrated. The RAT 10 includes a rotatable hub module 14 having two or more blades 16 configured to transmit a rotation to the rotating hub module 14 when it is exposed to an airflow identified by the arrow A. A first end 18 of the Support 12 is attached to a housing 19 which rotatably contains a drive shaft (not shown) attached to a rotating hub module 14. Rotation is transmitted to the drive shaft as the rotating hub module 14 rotates. . The RAT 10 is intended for emergency use as an impulse for a means of power generation, and has a stored, inactive position, illustrated by the dotted lines, and an active position, deployed, illustrated by the lines solid. In the stowed position, the RAT 10 is stored in a compartment 22 inside the fuselage of the aircraft 20, and a contour of both the fuselage of the aircraft 20 and the compartment 22 is schematically illustrated by dotted lines. In the deployed position, the RAT 10 is moved out of the compartment 22 to a position in which the blades 16 can rotate freely without interference from the fuselage of the aircraft 20 or the compartment 22. [0014] The opposite second end 24 of the support 12 is mounted on a frame so that the support 12 is configured to pivot about a pivot axis X which is the axis of rotation of a shaft 26, to move the RAT 10 between the stored and deployed positions . In the non-limiting embodiment illustrated, the deployment mechanism 30 includes an actuator 32 in the form of a spring loaded hydraulic cylinder having a first end 34 attached to the support 12. A locking mechanism (not shown) may be added and configured to maintain the RAT 10 in the stowed position and can be moved manually or automatically to release the RAT 10 for movement to the deployed position. Once unlocked, the deployment mechanism 30, as well as gravity, causes the RAT 10 to move from a stowed position to an extended position. Due to the restrictive size of the compartment 22, the blades 16 are held in a predetermined rotational position by an indexing mechanism 36 when the RAT 10 is in the stowed position. As illustrated, the indexing mechanism 36 comprises an elongate cable 38 supported for lengthwise movement by a pair of opening hooks 40 attached to the carrier 12. The end 42 of the cable 38 adjacent the hub 14 includes a ratchet pin (not shown) configured to extend through an opening and locking blades 16 in a predetermined position. During the transition from the stowed position to the deployed position, the carrier 12 rotates about a pivot axis X thereby applying a force to the cable 38 causing the ratchet pin to separate from the corresponding opening. A hub face 50 is placed in the most advanced part of the rotary hub module 14 so that a base 51 of the hub face 50 is mounted in a plane P substantially perpendicular to the direction of passage of the hub. an adjacent airflow, identified by the arrow A (see FIGs 3a-e). As illustrated in FIG. 2, the hub face 50 of the rotary hub block 14 has a generally flat surface placed in contact with the air flow A. Referring now to FIGS. 3a-3e, the shape or contour of the hub face 50 has been modified to minimize the surface area of the face of the hub 50 placed perpendicular to the flow direction of the air flow A according to an embodiment of the invention. By reducing the surface area of the hub face 50 oriented generally perpendicular to the airflow, the amount of ice accumulated thereon as the RAT 10 is deployed under adverse ambient flight conditions is minimized. The face of the hub 50 may comprise any of a variety of shapes configured to improve the aerodynamic capabilities of the RAT 10 while maintaining the characteristics that result in self-shedding of ice accumulated thereon. In various embodiments, as illustrated in FIGS. 3a and 3d, the face of the hub 50 can have a simple conical shape of varied proportions. In another embodiment, the face of the hub 50 has a frustoconical shape (FIG 3b) having two adjacent conical sections with varying angles. Furthermore, the face of the hub 50 may have a generally "coniptical" shape, as illustrated in FIG. 3c. A coniptic shape includes a first conical section 52 having a substantially round section, and a second section 54 having a substantially elliptical section. In such embodiments, the first section 52 may extend over any portion of the axial length of the hub face 50, such as, for example, 50%. In embodiments in which the face of the hub 50 has a generally angular shape, such as in FIGS. 3a-3d, e.g., the angle α of the upstream portion 56 of the face of the hub 50 configured to contact the airflow can vary from 30 ° to 60 °. Ice shedding is usually maximized when the angle a is about 45 °. However, because of the restrictive size envelope of the compartment 22, a compromise between ice shedding efficiency and overall aerodynamic performance would be required to properly implement certain shapes, eg, such as the "coniptic" shape. . In yet another embodiment, illustrated in FIG. 3rd, the face of the hub 50 has a convex shape generally rounded. A surface treatment or a glaciophobic coating may be applied to at least a portion of the exposed outer surface 58 of the face of the hub 50. Examples of glaciophobic coatings based on polydimethylsiloxane compounds (PDMS) infused with silicone- oil, epoxy silicone blends, and fluorine-modified polyesters, urethanes, or other suitable compositions. The glaciophobic coating is not only configured to prevent the formation of ice, but also to repel small water droplets at subzero temperatures, eg from rain, fog or melted snow . Preventing the accumulation and coagulation of such water-laden droplets results in successful anti-icing of the desired surface 58. In addition, or in addition to the glaciophobic coating, a light elastomeric material can be applied to the face. hub 50 to assist in shedding ice formed thereon as shown in FIGS. 4 and 5. Examples of lightweight elastomeric materials include neoprene, rubber and viton, in addition to any other suitable material. The elastomeric material is flexible under the weight of the ice. Thus, the elastomeric material will deform or become "twisted" due to the centrifugal forces acting upon rotation, thereby breaking the bonds formed between the surface of the elastomeric material and the accumulated ice.
    [0004] In one embodiment, the elastomeric material 60 is applied to the upstream portion or tip 56 of the face of the hub 50 configured to initially contact an airflow identified by the arrow A. Since the ice does not build up symmetrically on deforming rotating surfaces, ice can be easily relieved during bending / twisting of the rubber tip. Furthermore, or in addition, thin strips of elastomeric material 60 may be added around the surface 58 of the face of the hub exposed to the flow of air A to form a concentrator of stresses in the ice accumulated on it. this. The elastomeric material 60 is positioned around the face of the hub 50 in a relatively tight arrangement to limit the size of the ice pieces formed between the adjacent stress concentrators. In combination with the aerodynamic thrust from the airflow, these stress concentrators are designed to more easily cause the breaking of ice accumulated on it. In addition, the strips of elastomeric material 60 are generally placed around the hub face 50 in a symmetrical arrangement to maintain a balanced rotation of the hub module 14. For example, the elastomeric strips 60 may be laid in concentric circles, as shown in FIG. 5a, or otherwise, the elastomeric strips 60 may be laid in a spiral configuration extending from the upstream portion or the tip 56 as shown in FIG. 5b. Other arrangements of the elastomeric material 60 configured so that the accumulated ice breaks into small pieces are also within the scope of the invention. By modifying the contour of the hub module 50 of the RAT 10 to reduce the surface area thereof which is exposed to a flow of air, the amount of ice accumulation on the RAT 10 is reduced and the ice is more effectively relieved by the rotation of the hub module 14. Since the amount of accumulated ice is lower, any ice debris released by the hub swivel can represent a minimal risk of damage to the components and subsystems downstream of the ATR. Therefore, the RAT 10 no longer needs electrical heating in the region of the face 50 or hub surface 58 to melt the ice accumulated thereon. However, RAT 10 disclosed herein may be used in combination with one or more heaters. In addition, the ice particles shed from the face of the hub 50 are small and since the centrifugal force acting on the particles is high, the particles are ejected at a greater distance and therefore have less risk of damaging the components. downstream of the RAT 10. While the invention has been described in detail with respect to only a limited number of embodiments, it should be readily understood that the invention is not limited to such modes. disclosed. The invention may, rather, be modified to incorporate any number of variations, modifications, substitutions or equivalent arrangements not yet described herein, but which are consistent with the spirit and scope of the invention. the invention. In addition, although various embodiments of the invention have been described, it should be understood that aspects of the invention may include only some of the described embodiments. Therefore, the invention should not be construed as being limited by the foregoing description, but it is only limited by the scope of the appended claims.
    权利要求:
    Claims (13)
    [0001]
    Claims: 1. A dynamic air turbine (10) removable between a stowed position and an extended position, comprising: a rotatable hub module (14); a face (50) at a first end of the rotary hub module (14), the hub face having a non-planar configuration so that a limited portion of the surface area of the hub face is placed in a plane oriented perpendicular to a direction of passage of an air flow upstream of the face of the hub when the dynamic air turbine is in the deployed position.
    [0002]
    The dynamic air turbine (10) according to claim 1, wherein the face (50) of the hub has an angular shape.
    [0003]
    The dynamic air turbine (10) according to claim 2, wherein the angle of the upstream portion of the hub face (50) is configured to contact the airflow is between 30 ° and 60 ° .
    [0004]
    The dynamic air turbine (10) according to claim 2 or 3, wherein the face (50) of the hub has a conical shape.
    [0005]
    The dynamic air turbine (10) according to claim 2 or 3, wherein the face (50) of the hub has a frusto-conical shape.
    [0006]
    The dynamic air turbine (10) according to claim 2 or 3, wherein the hub face (50) has a coniptic shape.
    [0007]
    The dynamic air turbine (10) according to claim 1, wherein the face (50) of the hub has a rounded convex shape.
    [0008]
    The dynamic air turbine (10) according to any one of the preceding claims, wherein a glaciophobic coating is applied to the hub face (50) to minimize ice build-up thereon.
    [0009]
    The dynamic air turbine (10) according to any one of the preceding claims, wherein an elastomeric material (60) is applied to a portion of the hub face (50).
    [0010]
    The dynamic air turbine (10) of claim 9, wherein the elastomeric material is applied to an upstream end (56) of the hub face (50).
    [0011]
    The dynamic air turbine (10) according to claim 9 or 10, wherein the elastomeric material (60) is symmetrically wound around an exposed surface (58) of the hub face (50). 10
    [0012]
    The dynamic air turbine (10) according to claim 9, 10 or 11, wherein the elastomeric material (60) is applied in concentric circles.
    [0013]
    The dynamic air turbine (10) according to claim 9, 10 or 11, wherein the elastomeric material (60) is spirally applied.
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    同族专利:
    公开号 | 公开日
    US20160122034A1|2016-05-05|
    US10099772B2|2018-10-16|
    FR3027878B1|2018-10-19|
    引用文献:
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    US10322815B1|2018-03-22|2019-06-18|Hamilton Sundstrand Corporation|Stored electrical energy assisted ram air turbinesystem|
    US10661913B2|2018-04-30|2020-05-26|Hamilton Sundstrand Corporation|Hybrid ram air turbine with in-line hydraulic pump and generator|
    US20190360399A1|2018-05-25|2019-11-28|Rolls-Royce Corporation|System and method to promote early anddifferential ice shedding|
    法律状态:
    2016-09-21| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-30| PLSC| Search report ready|Effective date: 20170630 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/530,180|US10099772B2|2014-10-31|2014-10-31|Ice-shedding spinner for ram air turbine|
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